Pulsed Plasma Thrusters (PPTs) are a type of electric propulsion system that use pulsed plasma discharges to generate thrust. The thrust force in a Pulsed Plasma Thruster can be described using the basic rocket thrust equation.
PPTs are known for their simplicity and reliability, making them suitable for small satellites and spacecraft for attitude control and station-keeping. However, they typically have lower thrust compared to other electric propulsion systems. Detailed analysis and optimization of Pulsed Plasma Thrusters involve considerations of plasma dynamics, electromagnetic fields, and energy transfer mechanisms.
The thrust equation for a turbojet engine using control volume analysis is expressed as:
where,
- is the thrust force,
- ṁe is the mass flow rate of exhaust gases in kilograms per second (kg/s).
- is the Exhaust velocity at the nozzle exit in meters per second (m/s).
- ṁ0 is the mass flow rate of inlet gases in kilograms per second (kg/s).
- is the Exhaust velocity at the nozzle Inlet in meters per second (m/s).
- is the Pressure at the nozzle exit in pascals (Pa).
- is the Pressure at the nozzle inlet in pascals (Pa).
- is the Area of the nozzle exit in square meters (m²).